Numerical Study of Unsteady Shock/boundary Layer Interaction Induced by a Blunt Fin PDF Download
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Author: Satoru Yamamoto
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Languages : en
Pages :
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Author: Satoru Yamamoto
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Languages : en
Pages :
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Author: Gerard Degrez
Publisher:
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Languages : en
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Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Author: David S. Dolling
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
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An experimental study has been made of blunt fin-induced shock wave turbulent boundary layer interactions. This type of interaction is known to be highly unsteady. The objective of this experiment was to determine the characteristics of the fluctuating surface pressure distribution and the parameters controlling it. Tests have been made using fins of different diameter, D, with incoming turbulent boundary layers varying in thickness, Delta, in the ratio of about 5:1. Measurements have been made on the fin centerline and up to four diameters outboard of it. All tests were made at a Mach number of 2.95 and a unit Reynolds number of 6.3 billion/m, and under approximately adiabatic wall conditions. The measurements show that very high intensity r.m.s. pressure levels occur--up to almost two orders of magnitude above that of the incoming boundary layer. The highest intensities occur on centerline ahead of the fin. Here, the r.m.s. pressure distribution is characterized by three distinct peaks which decrease at different rates with distance outboard. Even four diameters off centerline, the maximum r.m.s. value in the distribution is still an order of magnitude larger than that of the incoming boundary layer. Outboard of the centerline, the r.m.s. pressure level downstream of the freestream shock wave steadily decreases. Within a distance of six to eight diameters it is close to the undisturbed value. With different diameter fins and different boundary layers, the qualitative characteristics are the same. The quantitative results depend on the ratio D/Delta. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 260
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Author: Christopher John Atkin
Publisher:
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Category :
Languages : en
Pages :
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Author: Gérard Degrez
Publisher:
ISBN:
Category :
Languages : en
Pages : 138
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Author: Leon Brusniak
Publisher:
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Category : Leading edges (Aerodynamics)
Languages : en
Pages : 702
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Author: C.-M. Hung
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Category :
Languages : en
Pages :
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Author: Paul J. Barnhart
Publisher:
ISBN:
Category :
Languages : en
Pages : 472
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